Aeroplane



I. CARLSO N.

AEROPLANE.

APPLICATION FILED NOV. 6. i920.

2 SHEETS-SHEET I- Iaoented Feb. 7, 1922.

INSLE'NTDFE.

ATTDHNEY I I. CARLSON.

AEROPLANE.

APPLICATION FILED NOV. 6., 1920.

Patented Feb. 7, 1922.

2 SHEETS-SHEET 2.

I iMYENTUE.

UNITED STATES.

PATENT OFFICE.

rvm OABLSON, or momms'rna, MASSACHUSETTS, ASSIGNOB, or ONE-Tm m examommo, or LOWELL, mssaonusnr'rs, AND one-m To 301m may LYNCH, orraw'rucxn'r, nnonn 15mm).

AEBOPLANE.

Specification of Letters Patent.

Patented Feb. '7, 1922.

Application filed November 6, 1920. Serial No. 422,271.

. To all whom it may concern:

in my application for a United States patent filed October 27, 1919,Serial No. 333,559, allowed August 3, 1920.

The object of my invention is to improve the construction and operationof such an aeroplane whereby the actions of rising and descendingvertically and of flying are greatly facilitated.

My invention consists in the peculiar and novel construction andimprovements in such I anaeroplane, said new construction andimprovements being principally in the planes, top, front and rearrudders and in the means for operating the same, as will be more fullyset forth hereinafter and claimed.

Figure 1 is a top plan view of my improved aeroplane showing the movableside planes in the raised position for flying.

Fi re 2- is a vertical longitudinal sectiona view through the aeroplanetaken on line 2, 2 of Figure 1, and

Figure 3 is a front view of the aeroplane showm the movable side planesin the lowere position, in broken lines, for rising or descendingvertically and in the raised position in full lines for flight.

In the drawings 4 indicates the fuselage, 5 the central plane, 6, 6 theside planes, 7 the top rudder, 8 the front rudder, 9 the twin rearrudder, 10 the engine, 11 the tractor shaft on which is a tractor helix12, 13 the propeller shaft on which is a propeller helix 14; and 15 thetransmission of my improved aeroplane.

The fuselage 4 consists of a suitable frame 16 as' shown, supporting theengine 10, wheels 17, 17, tractor bearinglS, propeller bearing 19,central plane 5, side planes 6, 6, transmission 15 and operators seat 20and the frame terminates in a front overhanging end 21 and a rearoverhangin end 22.

The central plane 5 is tent s. aped in cross section. It extends thelength of the fuselogo 4 and the slopes 23, 23 of the plane form on theunderside of the plane an inverted flattened V shape trough '24 whichextends the length of the plane. This central plane 5 is rigidly securedto the frame 16.

The side planes 6, 6 are each in the form of a flat rectan lar shapedplane. They extend the length of the central plane 5 on each side andare hinged at their inner edges at 25,25, to the frame 16, as shown inFigure 3 and form a continuation of the central plane 5. The width ofthese side planes is such that when in the lowered position for risingor descending the outer edges of the planes come at approximately thecenter of the wheels 17, 17. The side planes are operated by a handlever 26 to raise or lower the side planes. This hand lever 26 1s plvotly secured to the frame 16 in a convenient position to the operatorsseat 20, as shown in Figure 2. From this hand lever 26 rods 27, 27extend to pivot connections 28, 28, on the side planes 6, 6, as shown inFi re 3. i

he top vertical rudder 7 is flat and elon- .gated in form, it ispivotally secured adjacent its forward end to the frame 16, at 29 on topof the central plane 5 and extends centrally lengthwise of the centralplane. It is operated to steer the aeroplane sidewise by wires 30, 30which are secured at one end to each side of the top rudder 7. Each wire30, 30 extends down over pulleys 31, 31 and then to a foot treadle 32 onthe frame 16 in a convenient position for the foot of the operator, asshown in F i res 2 and 3.

The front rudder 8 is at and semi-circular in form. It'is pivotallysecured at 33in a horizontal position, to the end of the front overhan'ng end 21 of the frame 16. It is operate to steer the aeroplane up ordown by wires 34, 34, which are secured at one end to the rudder and attheir other ends to a hand lever 35 pivotally secured to the frame 16 ina-convenient position to the operators seat 20, as shown in Figure 2.

The twin rear rudder 9 consists of a horizontal rudder 36 and a'verticalrudder 37. The horizontal rudder 36 is the same as the front rudder 8,it is pivotally secured at 38 to the end of the overhanging end 22 ofthe frame 16. It is o erated to steer the aeroplane up or down y wires39, 39 which are secured at one end to the horizontal rudder 36 and attheir other ends to a hand lever 40, pivotally secured tothe frame 16 ina convenient position to the operators seat 20. The vertical rudder 37is pivotally secured at 41 to the horizontal rudder 36 and it has a slot42 through which the horizontal rudder 36 extends, whereby thehorizontal and vertical rudders have independent move-- ments. Thevertical rudder 37 is operated to steer the aeroplane sidewise by wires43, 43 which are secured at one end to the vertical rudder 37. Thesewires 43, 43 extend over pulleys 44, 44 and then downwards to a foottreadle 45 to which they are secured, the foot treadle 45 being in aconvenient position to the operators seat 20, as shown in Figure 2.

The engine 10 is secured to the frame 16, it may be of any well knownform of a gas engine supplied with fuel by a ipe 46 from an overheadfuel tank 47. Tile engine is operated in the usual way not shown fromthe operators seat 20.

The transmission 15 is operatively connected to a power shaft 48 whichis operatively connected to the engine 10. On the forward end of thepower shaft 48 is secured a bevel gear 49 meshing with a bevel gear 50on an inclined shaft 51 rotatably supported in bearings 52, 52 on theframe 16. On the forward end of the shaft 51 is a bevel gear 53 meshingwith a bevel gear 54 on the tractor shaft 11, thereby transmitting powerfrom the engine 10' to the tractor shaft 11. 1

The tractor shaft 11 is rotatably supported in the tractor shaft bearing18 and has fixed on its forward end' the tractor helix 12 andthehtractor shaft revolves preferably to the rig t.-

On the rear end of the ower shaft 48 is secured a bevel gear 55 mes ingwith a bevel gear 56 on a vertical shaft 57 rotatably supp)orted inbearings 58, 58 on the frame 16.

n the upper end of the vertical shaft 57 is a bevel gear 59 meshing witha bevel gear 60 on the propeller shaft 13, rotatably supported in thepropeller shaft bearing 19, thereby transmitting power from the engine10 to the propeller shaft 13.

The transmission 15, on the power shaft 48, is operated to control thesame by a hand lever 61 adjacent the operators seat 20 as shown inFigure 2. The construction of the transmission, not shown, is such thatthrough the operation of the hand lever 61 the tractor helix 12 and thepropeller helix 14 may be made to revolve simultaneously to the right topropel the aeroplane in a forward direction, or the tractor helix 12 maybe made to revolve simultaneously to the right and the propeller helix14 simultaneously to the left to raise the aeroplane vertically upwards.The operations of the tractor and propeller helixesare the same as in myprevious patent application and any form of a I transmission may beused,.that will accomplish the same result. A

As hown in Figure 3 the central plane 5 is concaved in cross section andforms a flat tened V shaped trough 24 on its under side and whichextends the le h of the central plane. The aeroplane w en moving forwardin the air moves in the direction of the arrow62, as shown in Figure 2and when moving vertically upwards in the direction of (phe arrows'63 63as shown in Figures 2 an 3.

When in use and it is desired to arise vertically upwards, the operatorseats himself in the operators. seat 20 and then operates thetransmission 15 by the hand lever 61, so that the tractor helix 12 willrevolve to the right to move the aeroplane forward, and the propellerhelix 14 to the left, to move the aero lane backwards. He then operatesthe hall lever 26 to close the side planes 6, 6 into position, as shownin broken lines in Figure 3. The to rudder 7, front rudder 8 an reartwin ru der 9, being in a central or neutral position, as shown in fulllines in the figures, the operator now starts the engine 10 in the usualway. The helixes revolving in the directions stated, cause blasts of airto meet in the center. portion of the trough'24 on the underside ofthe'central plane 5 and forces the central plane 5 and tral plane 5 andcoming together, at the central portion of the plane are forceddownatmosphere, also. 1n conjunction with the first blasts of airagainst the plane, forces the aeroplane upwards. With the' side planes6, 6 closed as shown in broken lines 1n Figure 3, the blasts of air aremore confined to a downward direction and a better ,wards and forming anair pack against the operated b the hand lever 61 so that the tractor anpropeller helixes will both revolve to the right, both helixes nowrevolve in the same direction and at the same speed. As the helixes arenow revolving on the same plane, or center line of the aeroplane, in thesame direction and at the same speed, the speed of the engine ma now beincreased to its maximum s eed. en it is desired to alight vertical poonthe ground or other structures, the a ve operations are reversed.

My present invention lies more particularlpk in new construction andoperation such as t e central tent shaped plane 5, the movable sideplanes 6, 6 the top rudder 7 the twin rear rudder 9 and the frame 16.

Having thus described my invention I claim as new 1. An aeroplane havinga frame, a central plane extending lengthwise of the frame and formed tohave a flattened V shaped trough on its underside and extending thelength of the plane, said plane bein secured to the frame, rectangularshaped side planes hinged to the'frame and extending the length of thecentral plane, means for 0 erating the side planes, a top rudder pivotaly secured to the frame over the central plane,-means for operating thetop rudder, a front horizontal rudder hinged to the frame, means foroperating the front rudder, a twinrear rudder comprising a horizontalrudder hinged to the frame and a vertical rudder pivoted to thehorizontal rudder, means for operating{ the twin rear rudder, an enginesupporte by the frame, a tractor shaft rotatably supported in bearingsin the frame and operatively connected with the engine, a tractor helixon the tractor shaft at the forward end of the central plane, apropeller shaft rotatably supported in bearings, a propeller he lix onthe propeller shaft at the rear end of the central plane, a transmissionoperatively connected with the tractor and propeller shafts, and meansfor operating the trans.- mission, for the purpose as described.

2. An aeroplane having a frame with overhanging front and rear ends, arectangular shaped central plane extending lengthwise of the frame andhaving a flattened V shaped trough on its underside and extending thelength of the plane, being secured to the frame, rectangular shaped sideplanes hinged to the frame and extending the length of the central planeand forming a continuation of the central plane, means for operating theside planes, a rectangular shaped vertical top rudder over the centralplane and pivotally secured to the frame, means for o crating the toprudder, a semi-circular ront horizontal rudder hinged to the frontoverhangin end of the frame, means for operating the front rudder, atwin rear rudder comprising a semi-circular horizontal rudder hinged tothe rear overhanging end of the frame and a vertical rudder pivoted tothe horizontal rudder, said vertical rudder havin a slot through whichthe horizontal ru der extends, means for operatin "the twin .rearrudder, an engine su porte by the frame, a tractor helix at theorwardend of the central plane and operativel connected with the engine,a propeller helix at the rear end of the frame, and operativelyconnected with the engine, a transmission operatively connecting theengine with the tractor and propeller helixes and means for operatingthe transmission, for the pur ose as described.

In testimony whereof, have signed my name to this specification.

IVAR CARLSON.

said plane

